In orbit space transportation and recovery system

Abstract

An In Orbit Transportation & Recovery System (IOSTAR™) ( 10 ) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor ( 19 ). The IOSTAR™ includes a collapsible boom ( 11 ) connected at one end to a propellant tank ( 13 ) which stores fuel for an electric propulsion system ( 12 ). This end of the boom ( 11 ) is equipped with docking hardware ( 14 ) that is able to grasp and hold a satellite ( 15 ) and as a means to refill the tank ( 13 ). Radiator panels ( 16 ) mounted on the boom ( 11 ) dissipate heat from the reactor ( 19 ). A radiation shield ( 20 ) is situated next to the reactor ( 19 ) to protect the satellite payload ( 15 ) at the far end of the boom ( 11 ). The IOSTAR™ ( 10 ) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

1. An apparatus comprising:
 a boom means ( 11 ) for providing support; 
 a nuclear reactor means ( 19 ) for generating heat; said nuclear reactor means ( 19 ) being coupled to said boom means ( 11 ); 
 a payload protection means ( 20 ) for protecting a payload ( 15 ) from radiation; said payload protection means ( 20 ) being coupled to said nuclear reactor means ( 19 ); 
 a radiator means ( 16 ) for dissipating heat; said radiator means ( 16 ) being coupled to said nuclear reactor means ( 19 ); 
 an electric propulsion means ( 12 ) for supplying thrust; said electric propulsion means ( 12 ) being coupled to said nuclear reactor means ( 19 ); 
 a propellant tank means ( 13 ) for storing fuel for said electric propulsion means ( 12 ); 
 said propellant tank means ( 13 ) being coupled to said boom means ( 11 ); and 
 a multiple-use grasping means ( 14 ) for interacting with a plurality of different objects and being configured to partially surround one of said plurality of different objects; said grasping means for engaging and grasping said object without the need for any preconfigured docking interface on said object; said grasping means ( 14 ) extending outwardly at one end away from said boom means ( 11 ); said grasping means ( 14 ) being coupled to said boom means ( 11 ), generally at one end of said boom means ( 11 ). 
 
   
   
     2. An apparatus as recited in  claim 1 , in which said nuclear reactor means ( 19 ) includes a Brayton Cycle energy converter. 
   
   
     3. An apparatus as recited in  claim 1 , in which said payload protection means ( 20 ) includes a recuperator. 
   
   
     4. An apparatus as recited in  claim 3 , in which said recuperator is employed as a gamma shield. 
   
   
     5. An apparatus as recited in  claim 3 , in which said recuperator is cooled by a thermoelectric cooler. 
   
   
     6. An apparatus as recited in  claim 1 , which may be controlled from an on-orbit controller. 
   
   
     7. An apparatus as recited in  claim 1 , further comprising a laser used for orbital debris removal. 
   
   
     8. An apparatus as recited in  claim 1 , which is used to produce propellant from an asteroid. 
   
   
     9. An apparatus as recited in  claim 8 , in which ice present on said asteroid is electrolyzed to form hydrogen and oxygen. 
   
   
     10. An apparatus as recited in  claim 8 , in which a carbonaceous material present on said asteroid is processed to form a storable propellant. 
   
   
     11. An apparatus as recited in  claim 1 , in which a propellant is produced from water launched into orbit from Earth. 
   
   
     12. An apparatus as recited in  claim 1 , in which a propellant is produced from a stable, storable material launched into orbit from Earth. 
   
   
     13. An apparatus as recited in  claim 1 , further comprising:
 a conductor ( 21 ); said conductor ( 21 ) for generating an electrical current. 
 
   
   
     14. Apparatus as recited in  claim 13 , in which said conductor ( 21 ) is coupled to said boom ( 11 ). 
   
   
     15. An apparatus as recited in  claim 13 , in which said conductor ( 21 ) is coupled to said radiator ( 16 ). 
   
   
     16. An apparatus as recited in  claim 13 , in which said electrical current is consumed. 
   
   
     17. An apparatus as recited in  claim 13 , in which said electrical current is conveyed to another satellite. 
   
   
     18. An apparatus as recited in  claim 13 , in which an opposite electrical current is imparted into said conductor ( 21 ) to change the orbit of a satellite. 
   
   
     19. An apparatus as recited in  claim 18 , in which said opposite electrical current is used to deorbit a satellite. 
   
   
     20. An apparatus as recited in  claim 13 , further comprising:
 a plasma contactor ( 23 ); said plasma contactor ( 23 ) being coupled to said conductor ( 21 ). 
 
   
   
     21. An apparatus as recited in  claim 20 , in which said plasma contactor ( 23 ) is a hollow cathode assembly.